Guided missile

ABSTRACT

1. An aerial missile including, in combination, an airframe comprising a plurality of connected body assemblies having duct sections defining a duct extending throughout the length of the body and having a wall, said wall providing an inlet, a diffuser communicating with the inlet, a combustion chamber communicating with the diffuser and an exit nozzle communicating with the combustion chamber, a cowl lip connecting the forwardmost body assembly and the wall of the forwardmost duct section at their corresponding forward ends, wings on the airframe and mounted for rocking movement about their root axes, longitudinally spaced partitions surrounding the duct wall and defining a compartment, an explosive charge in the compartment and surrounding the duct, a fuze system for the charge, and means mounted on one of the partitions and operable for imparting rocking movement to the wings.

United States Patent [191 Goss et al.

1 51 Sept. 30, 1975 1 GUIDED MISSILE [73] Assignee: The United States ofAmerica as represented by the Secretary of the Navy, Washington, DC.

[22] Filed: June 26, 1956 [21] App]. No.: 594,067

[52] US. Cl 244/321; 60/270 [51] Int. Cl. F42B 15/02 158] Field ofSearch 244/14. 3.21; 114/201;

[56] References Cited UNITED STATES PATENTS 2.459.009 1/1949 Wallis244/36 2.557.401 6/1951 Agins 244/311 2.603.434 7/1952 Merrill. 244/1142.690.314 9/1954 Porter 244/311 2.744.697 5/1956 Van Allen.. 244/3.152745.095 5/1956 Stoddard... 244/3.l3

2.769.601 1 1/1956 Hagopian 244/14 2.818.914 1/1958 Thomann ct a1 114/202.82-1.71 1 3/1958 Porter 244/321 2.873.074 2/1959 Harris et a1. 244/3212.915.747 12/1959 Segerstrum 343/73 FUEL ensssumzmou 22a JAILFIPE [$8COMBUSTOR [B TRACKING FLARE HOLDER [D 2002 BEAM RIDING WAVE GUIDE 2030TELEMETERING NOTCR ANTENNAE I78 I FIN [/7 a 54 gr: 144 28g 2.996.7078/1961 Hirsch 343/73 OTHER PUBLICATIONS TMa-l9852/to39B-1A-9, Depts. ofArmy & Air Force, Mar. 1953, pp. 218232.

Radar Guided Missile, Wireless World, Feb. 1956, pp. 67-70.

Primary E.\'aminerVerlin R. Pendegrass Attorney. Agent, or FirmR. S.Sciascia; J. S. Lacey; W. G. Finch EXEMPLARY CLAIM 1. An aerial missileincluding, in combination, an airframe comprising a plurality ofconnected body assemblies having duct sections. defining a ductextending throughout the length of the body and having a wall. said wallproviding an inlet. a diffuser communicating with the inlet, acombustionchamber communicating with the diffuser and an exit nozzle communicatingwith the combustion chamber, a cowl lip connecting the forwardmost bodyassembly and the wall of the forwardmost duet section at theircorresponding forward ends. wings on the airframe and mounted forrocking movement about their root axes. longitudinally spaced partitionssurrounding the duct wall and defining a compartment, an explosivecharge in the compartment and surrounding the duct, 21 fuze system forthe charge, and means mounted on one of the partitions and operable forimparting rocking movement to the wings.

Claims, Drawing Figures STATIC PRESSURE PROBE I26 FUEL TANK "ZLDRAULICSVS 2Z0 STEERING INTELLSYS. 212

, rt ist cou rggt CONTROL svstsm 2/4 $225,? FUZE svs'rsu- 5 POWER svsrsuz/s WING I13 ,runamz AIR INYAKE srnur 4 FETY a mums/.52 mums marzmuz I24muznmmr RA" PRESSURE PROBE I28 US. Patent Sept. 30,1975 Sheet3of593,908,933

m T N E V m ATTORNEY wmw vmw US. Patent Sept.30,1975 Sheet40f593,908,933

I NVENTOR ATTORNEY US. Patent Sept. 30,1975 Sheet50f59 3,908,933

U.S. Patent Sept.30,1975 Sheet90f59 3,908,933

FIG. 12.

532 gllllfi llllig A 0,

mull") I if FUEL INLET -FROM FUEL SHUT-OFF VALVE //4" STEEL LOCKINGBALLS 722 PREc'sloN SPRING 0 cowsmm' TORQUE THUMB scar-1w *wmw VALVEPENING SPRING 7/8 LOCKING GROOVE 738-FOR OPEN POSITION 4 725$ OPENPas/7,0

INVENTOR FUEL SHUT-OFF VALVE ATTORNEY US. Patent Sept. 30,1975 Sheet 100f59 3,908,933

FIG/4.

NITROGEN FLOW CONTROL UNIT Fuel Pressurizafl'an System 560 SURGEPREVENTATIVE PISTON 44.9

FRO/"NITROGEN TANK 448 580 x k k 21%HMHHHHHHHH Tumm- RA M PRESSURE INVENTOR ATTORNEY US. Patent S apt. 30,1975

308 FIG. /6.

HYDRAULIC SYSTEM (Packag/ng Arrangemenf) FORWARD ACCUMULATOR BOD! STATICPRESSURE LINE FUEL SHUT-OFF VALVE wme LOCK FILTERS TORQUE MOTOR FILLPLUG RETUR V HYDRAULEJEST CONNEfTIONS I LOOK TEST CONNECTIONS HYDRAULICPRESSURE GAGE HYDRAULIC SUMP FQRWA R0 Sheet 12 of 59 PILOT REGULATORI382 wme ACTUATOR wms ACTUATOR I C WING /I2 1-.

IN VENTOR ATTORNEY U..S. Patent Sept. 30,1975 Sheet 13 0f 59 FIG. [7

HYDRAULIC SYSTEM (Packag/ng Arrangement) HYDRAULIC SUMP TURBINE A RINTAKE wms ACTUATOR I I I 1 I383 WING ACTUATOR O WING LOCK I40 Ts/QESEERACCUMULATOR E I922 FILTER HYDRAULIC PUMP INVENTOR ATTORNEY US. PatentSapt.30,1975 Sheet 14 of59 3,908,933

FIG. 18. E0

HYDRAU LIG SYSTEM (Packaging Arrangemenl} NITROGEN SUPPLY FOR FUELPRESSURIZATION BLADDERS MANIFOLD HYDRAULIC PUMP I390 TURBINE AIR INTAKEc WING //4 l.

wme LOCK WING ACTUATOR TRANSFER VALVE 4 cnzcx VALVE ggg ROLL RATE GYROI820 THREE WAY SOLENOID 450 cNEcK VALVE I385 8 206/ wme ACTUATOR A a 5RATE GYROS 308 FROM RAM AIR AT TURBINE FUEL PUMP IN VENTOR ATTORNEY US.Patent Sept .30,1975 Sheet 15 0f59 3,908,933

FIG. [9.

HYDRAULIC SYSTEM (Packaging Arrangement) I384 wms ACTUATOR TO FUELPRESSURIZATION BLADDERS MANIFOLD TORQUE MOTOR A 8 8 RATE GYROS WAYSOLENOID VALVE TORQUE MOTOR 1 CHECK VALVE I TRANSFER VALVE I C WING [I5L WING ACTUATOR FUEL REGULATOR FUEL PUMP TO RAM PRESSURE PROBE INVENTORATTORNEY US Patent Sept. 30,1975 Sheet 16 of 59 FROM NITROGEN SUPPLYWING 1/4 NOTE:

FOR PURPOSE OF CLARITY THE FLEXIBLE FLUID LINES SUPPLYING THE HYDRAULICWING AGTUATORS HAVE D W Y F L w n m w M E N U A E L m T B U A WING //3WING [/2 INVENTOR ATTORNEY wme RETAINING SLEEVE 34/ FIG. 2/.

US Patsnt Sept. 30,1975 Sheet 18 of59 3,908,933

US. Patent Sept. 30,1975 Sheet 19 of 59 3,908,933

1. An aerial missile including, in combination, an airframe comprising apluralIty of connected body assemblies having duct sections defining aduct extending throughout the length of the body and having a wall, saidwall providing an inlet, a diffuser communicating with the inlet, acombustion chamber communicating with the diffuser and an exit nozzlecommunicating with the combustion chamber, a cowl lip connecting theforwardmost body assembly and the wall of the forwardmost duct sectionat their corresponding forward ends, wings on the airframe and mountedfor rocking movement about their root axes, longitudinally spacedpartitions surrounding the duct wall and defining a compartment, anexplosive charge in the compartment and surrounding the duct, a fuzesystem for the charge, and means mounted on one of the partitions andoperable for imparting rocking movement to the wings.
 2. An aerialmissile as recited in claim 1, wherein said means includes a pluralityof hydraulically operated wing actuators, one of said actuators beingprovided for each said wing, a source of hydraulic fluid under pressureconnected to said actuators, means for controlling flow of fluid to saidactuators in response to an electrical signal, and links mechanicallyconnecting the actuators to the wings.
 3. In combination with an aerialmissile having an airframe including a center body assembly, wingsmounted for rocking movement on said body assembly, and means forboosting the missile to supersonic speed; hydraulically operated meanswithin the missile and operable for imparting movement to the wings,said hydraulically operated means including a source of hydraulic fluid,a pump, a plurality of wing actuators, a turbine for operating the pump,means for supplying air under pressure to the turbine during flight ofthe missile, linkages connecting the actuators with the wings, valvemeans for controlling fluid flow to the actuators, and electricallyoperated means for controlling the valve means.
 4. In combination withan aerial missile having an airframe comprising connected bodyassemblies, wings mounted for rocking movement on one of the bodyassemblies, guidance apparatus in the missile and producing electricalvoltages representing missile position errors, and booster means foraccelerating the missile to supersonic speed; hydraulically operatedmeans within the missile and operable for imparting movement to thewings, said means including a source of hydraulic fluid under pressurewithin the missile, a pump, a plurality of wing actuators, a turbine foroperating the pump, means for supplying air under pressure to theturbine during flight of the missile, linkages connecting the actuatorswith the wings, valve means for controlling fluid flow to the actuators,and electrically operated means connected with the guidance apparatusand responsive to said electrical voltages for controlling said valvemeans, whereby said actuators will be operated by said fluid flow forshifting the wings to correct for said position errors.
 5. Thecombination recited in claim 3, including means for locking the wingsduring operation of the booster means, said wing locking means beingreleasable upon termination of operation of the booster means.
 6. Thecombination recited in claim 3, including additionally means for lockingthe wings during operation of the booster means, said wing locking meansincluding a cylinder mounted in the missile adjacent each wing, saidwing having a recess, a locking pin having a piston movable in thecylinder, a spring normally urging one end of the pin into the recessfor locking the wing, a solenoid operated valve, fluid connectionsbetween the solenoid operated valve, the cylinder and the hydraulicmeans, a source of electric power for the solenoid valve, and means forconnecting said electric power source to the solenoid of the solenoidoperated valve for opening said valve upon separation of the boostermeans from the missile whereby fluid will flow to the cylinder forshifting the piston against the compression of the spring andwithdrawIng the locking pin from the recess for unlocking the wing. 7.The combination recited in claim 6, including additionally meansoperable for releasing the wings, whereby said wings may be detachedfrom the body assembly.
 8. In an aerial missile having an airframe and abody assembly, and wings mounted for rocking movement on the bodyassembly; means for mounting said wings for quick detachment from thebody assembly, said means including a wing mounting bulkhead in the bodyassembly for each wing, a wing retaining sleeve in the bulkhead, eachsaid wing having a spar mounted in the sleeve, a bearing rotatablyconnecting the sleeve with the bulkhead, tongues on the sleeve, andlatches on the body assembly and engageable with the tongues.
 9. Thecombination recited in claim 4, wherein said last mentioned meansincludes torque motors for said valve means, each of said torque motorscomprising an armature, and a pair of coils surrounding the armature,said armature being movable in one direction by energization of one ofsaid coils and being movable in the opposite direction by energizationof the other of said coils.
 10. The combination recited in claim 4,wherein said missile airframe includes an inner body mounted within theforwardmost body assembly at its forward end, and said hydraulicallyoperated means includes an accumulator mounted in said inner body. 11.An aerial missile including, in combination, an airframe includingforward, center, and aft body assemblies each having a wall defining aduct section, said assemblies being connected in alignment whereby theduct sections thereof will define a continuous duct extending throughoutthe length of the missile, the wall of the duct being shaped to definean inlet, a diffuser, and an exit nozzle, and a combustor in the ductwithin the center and aft body assemblies and including an outer shroud,a central can within the outer shroud, a pilot fuel injector assemblysurrounding the central can at its forward end and fuel supply meansextending into the combustor and connected to the pilot fuel injectorassembly.
 12. An aerial missile as recited in claim 11, includingadditionally fuel injector means in the central can, a source of fuel inthe missile and positioned about the center body assembly, meansconnecting the fuel source with the fuel injector means, and fueligniter means in the combustor.
 13. A hydraulic system for a missilehaving a movable wing and a duct, comprising, a pump in the missile, aturbine in the missile and operable by airflow passing through the ductduring flight of the missile, a wing actuator in the missile andincluding a cylinder, a piston in the cylinder and having a piston rod,linkage means connecting the piston rod to the wing, means connectingthe wing actuator to the pump, a source of hydraulic fluid for the pump,the cylinder and for said last mentioned means, said pump forcing saidfluid through said last mentioned means into said cylinder for shiftingsaid piston and rod whereby said linkage will be moved for moving thewing, and means connected between said last mentioned means and saidcylinder for controlling fluid flow to the cylinder in response to anelectric signal.
 14. A hydraulic system as recited in claim 13, whereinsaid fluid flow controlling means comprises a transfer valve, and atorque motor operatively connected with the valve.
 15. A hydraulicsystem as recited in claim 13, including additionally means for lockingthe wing prior to operation of the turbine and pump.
 16. A hydraulicsystem as recited in claim 13, wherein the wing is formed with a recessat its root end, and including additionally means for locking the wingagainst movement prior to operation of the turbine and pump, said lastmentioned means including a cylinder, a locking pin having a pistonmovable in the cylinder, and a spring urging the pin into the recess.17. In a missile having an airframe including a body, and wings mountedfor rocking movement on the airframe; a hydraulic system in the missileand operative for imparting rocking movements to said wings, comprising,a turbine in the airframe, a pump driven by the turbine, a sump, a pairof accumulators, hydraulic fluid in the system, wing actuatorsoperatively connected with the wings, one said actuator being providedfor each wing and each said actuator including a cylinder, a piston inthe cylinder and means connecting the piston with the wing; fluidconductor means, and electrically operated valve means, said fluidconductor means being connected between the pump, accumulators, sump,wing actuators and valve means, operation of the pump causing fluid flowto the actuator cylinders under control of said valve means.
 18. Thestructure recited in claim 17, wherein said electrically operated valvemeans includes a transfer valve, and a torque motor for operating thetransfer valve.
 19. In an aerial missile having an airframe comprising aplurality of connected body assemblies each having a duct section, saidduct sections defining a continuous duct for the missile, saidcontinuous duct including a diffuser, a combustion chamber and an exitnozzle; a combustor in the combustion chamber and including an outershroud, a central can mounted axially within the outer shroud, a pilotfuel injector assembly mounted within the upstream end portion of theouter shroud and surrounding the upstream end of the central can andfuel supply means mounted axially of the combustion chamber andconnected to the pilot fuel injector assembly.
 20. A combustor for anaerial missile, comprising, an outer shroud, a central can mountedaxially within the outer shroud, a pilot fuel injector assembly mountedwithin the outer shroud and surrounding a portion of the central can,and fuel distribution means extending into the combustor axially of theshroud assembly and connected to the pilot fuel injector assembly.
 21. Acombustor as recited in claim 20, including igniter means extending intothe outer shroud in the vicinity of the fuel distribution means.
 22. Acombustor for an aerial missile, comprising, a frusto-conical outershroud, a central can mounted in the outer shroud, a pilot fuel injectorassembly mounted concentrically within the outer shroud, pilot fuelinjector means connected with the pilot fuel injector, main fuelinjector means, and means mounting the pilot injector means and maininjector means in spaced relation to each other within the shroud.
 23. Acombustor for an aerial missile, comprising, a frusto-conical outershroud having a downstream end presented away from a fluid flow, acentral can within the outer shroud, a pilot fuel injector assemblymounted concentrically within the upstream end portion of the shroud andsurrounding one end of the central can, fuel distribution meansconnected to the pilot fuel injector assembly near one end thereof, mainfuel injector means within the pilot fuel injector assembly andextending downstream of the pilot fuel injector means assembly, fuelsupply means for said pilot fuel injector assembly and for said mainfuel injector means, and igniter means mounted in the shroud upstream ofthe pilot fuel injector means.
 24. In combination with a aerial missilehaving an airframe having a diffuser, a combustor in the airframedownstream of the diffuser, and fuel injector means in the combustor; afuel system comprising a fuel tank, first fuel pressurization means inthe missile and connected with the tank for initially pressurizing fuelin the tank, a second fuel pressurization means in the missile forpressurizing fuel in the tank during flight of the missile and afterdecay of pressure from said first fuel pressurization means to apredetermined value, said second fuel pressurization means including ascoop mounted to receive air flow passing through the diffuser duringmissile flight, a pump, a turbine connected with the pump for drivingsaid pump, means connecting the pump with the scoop, and means forconnecting thE pump with the fuel injector means, operation of the pumpsupplying fuel to the injector means during flight of the missile. 25.The combination recited in claim 24 including additionally fuelregulator means connected with the pump, said last mentioned means andthe fuel injector means.